JP2017533369A - Self-stiffening casing made of composite material with organic matrix - Google Patents

Self-stiffening casing made of composite material with organic matrix Download PDF

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JP2017533369A
JP2017533369A JP2017510520A JP2017510520A JP2017533369A JP 2017533369 A JP2017533369 A JP 2017533369A JP 2017510520 A JP2017510520 A JP 2017510520A JP 2017510520 A JP2017510520 A JP 2017510520A JP 2017533369 A JP2017533369 A JP 2017533369A
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casing
stiffener
fiber
gas turbine
annular recess
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JP6734261B2 (en
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マラン セバスチャン
マラン セバスチャン
ダミアン ロンバール カンタン
ダミアン ロンバール カンタン
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サフラン エアークラフト エンジンズ
サフラン エアークラフト エンジンズ
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/06—Fibrous reinforcements only
    • B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
    • B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
    • B29C70/22—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
    • B29C70/222—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure the structure being shaped to form a three dimensional configuration
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/06—Fibrous reinforcements only
    • B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
    • B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
    • B29C70/24—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/32—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core on a rotating mould, former or core
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/40—Shaping or impregnating by compression not applied
    • B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
    • B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
    • B29C70/446—Moulding structures having an axis of symmetry or at least one channel, e.g. tubular structures, frames
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
    • D—TEXTILES; PAPER
    • D03—WEAVING
    • D03D—WOVEN FABRICS; METHODS OF WEAVING; LOOMS
    • D03D11/00—Double or multi-ply fabrics not otherwise provided for
    • D—TEXTILES; PAPER
    • D03—WEAVING
    • D03D—WOVEN FABRICS; METHODS OF WEAVING; LOOMS
    • D03D15/00—Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used
    • D03D15/20—Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used characterised by the material of the fibres or filaments constituting the yarns or threads
    • D03D15/242—Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used characterised by the material of the fibres or filaments constituting the yarns or threads inorganic, e.g. basalt
    • D03D15/267—Glass
    • D—TEXTILES; PAPER
    • D03—WEAVING
    • D03D—WOVEN FABRICS; METHODS OF WEAVING; LOOMS
    • D03D15/00—Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used
    • D03D15/20—Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used characterised by the material of the fibres or filaments constituting the yarns or threads
    • D03D15/242—Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used characterised by the material of the fibres or filaments constituting the yarns or threads inorganic, e.g. basalt
    • D03D15/275—Carbon fibres
    • D—TEXTILES; PAPER
    • D03—WEAVING
    • D03D—WOVEN FABRICS; METHODS OF WEAVING; LOOMS
    • D03D15/00—Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used
    • D03D15/20—Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used characterised by the material of the fibres or filaments constituting the yarns or threads
    • D03D15/283—Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used characterised by the material of the fibres or filaments constituting the yarns or threads synthetic polymer-based, e.g. polyamide or polyester fibres
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
    • B29B11/00—Making preforms
    • B29B11/14—Making preforms characterised by structure or composition
    • B29B11/16—Making preforms characterised by structure or composition comprising fillers or reinforcement
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/748—Machines or parts thereof not otherwise provided for
    • B29L2031/7504—Turbines
    • D—TEXTILES; PAPER
    • D10—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
    • D10B—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
    • D10B2101/00—Inorganic fibres
    • D10B2101/02—Inorganic fibres based on oxides or oxide ceramics, e.g. silicates
    • D10B2101/06—Glass
    • D—TEXTILES; PAPER
    • D10—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
    • D10B—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
    • D10B2101/00—Inorganic fibres
    • D10B2101/02—Inorganic fibres based on oxides or oxide ceramics, e.g. silicates
    • D10B2101/08—Ceramic
    • D—TEXTILES; PAPER
    • D10—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
    • D10B—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
    • D10B2101/00—Inorganic fibres
    • D10B2101/10—Inorganic fibres based on non-oxides other than metals
    • D10B2101/12—Carbon; Pitch
    • D—TEXTILES; PAPER
    • D10—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
    • D10B—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
    • D10B2403/00—Details of fabric structure established in the fabric forming process
    • D10B2403/03—Shape features
    • D10B2403/033—Three dimensional fabric, e.g. forming or comprising cavities in or protrusions from the basic planar configuration, or deviations from the cylindrical shape as generally imposed by the fabric forming process
    • D10B2403/0331—Three dimensional fabric, e.g. forming or comprising cavities in or protrusions from the basic planar configuration, or deviations from the cylindrical shape as generally imposed by the fabric forming process with one or more convex or concave portions of limited extension, e.g. domes or pouches
    • D—TEXTILES; PAPER
    • D10—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
    • D10B—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
    • D10B2505/00—Industrial
    • D10B2505/02—Reinforcing materials; Prepregs
    • D—TEXTILES; PAPER
    • D10—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
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    • D10B2505/00—Industrial
    • D10B2505/12—Vehicles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/14—Casings or housings protecting or supporting assemblies within
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/232—Three-dimensional prismatic conical
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
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    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F05D2300/6033—Ceramic matrix composites [CMC]
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/614—Fibres or filaments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
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    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/615—Filler
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
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    • F05D2300/00—Materials; Properties thereof
    • F05D2300/70—Treatment or modification of materials
    • F05D2300/702—Reinforcement
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Textile Engineering (AREA)
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  • Composite Materials (AREA)
  • General Engineering & Computer Science (AREA)
  • Inorganic Chemistry (AREA)
  • Moulding By Coating Moulds (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
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Abstract

本発明は、マトリックスで高密度化された繊維補強材から複合材料で作られているガスタービンケーシング（１０）に関する。このケーシング（１０）は、このケーシング（１０）の内側表面（１１）内に環状凹み（１７１）を形成するように、補剛材部分（１７）に隣接しているこのケーシングの上流部分及び下流部分（１８、１９）の半径よりも大きい半径において延びる少なくとも１つの補剛材部分（１７）を備える。【選択図】図２The present invention relates to a gas turbine casing (10) made of a composite material from a fiber reinforcement densified with a matrix. The casing (10) is upstream and downstream of the casing adjacent to the stiffener portion (17) so as to form an annular recess (171) in the inner surface (11) of the casing (10). At least one stiffener portion (17) extending at a radius greater than the radius of the portions (18, 19). [Selection] Figure 2

Description

本発明はガスタービンエンジンに関し、さらに特に、しかし非排他的に、航空機用エンジンのためのガスタービンファンケーシングに関する。   The present invention relates to gas turbine engines, and more particularly, but not exclusively, to gas turbine fan casings for aircraft engines.

ガスタービン航空機用エンジンでは、ファンケーシングが幾つかの機能を果たす。特に、ファンケーシングは、エンジンの中への空気入口通路を画定し、採用随意に、ファンのブレードの先端部に整合している摩耗性材料、及び／又は、エンジンの入口における音響的処置のための音波吸収装置構造を支持し、及び、滞留シールド（ｒｅｔｅｎｔｉｏｎ ｓｈｉｅｌｄ）を組み込むか又は支持する。   In gas turbine aircraft engines, the fan casing serves several functions. In particular, the fan casing defines an air inlet passage into the engine and is optionally employed for wearable material aligned with the tip of the fan blade and / or for acoustic treatment at the engine inlet. Support and support or support a retention shield.

ファンケーシングのようなケーシングは、通常は金属材料で作られているが、現在では、複合材料によって、即ち、有機マトリックスによって高密度化された繊維プリフォームで作られており、したがって、部品の総重量を、金属で作られる時の同一の部品の重量よりも軽量化することを可能にすると同時に、より良好ではないとしても少なくとも同等である機械的強度を実現する。有機マトリックス複合材料でファンケーシングを製造することがある特許文献に説明されている（例えば、特許文献１参照。）。   Casings such as fan casings are usually made of metallic materials, but are now made of composites, i.e. fiber preforms densified by an organic matrix, and thus the total of the parts. It makes it possible to make the weight lighter than the weight of the same part when made of metal, while at the same time achieving a mechanical strength that is at least equal if not better. It is described in a patent document in which a fan casing is manufactured with an organic matrix composite material (for example, see Patent Document 1).

複合材料ケーシングの使用がエンジンの総重量を減少させることを可能にするが、この重量の減少は、ケーシングの共振周波数を低下させ、及び、このことが、ファンのブレードからの乱気流（ｗａｋｅ）との干渉を結果的に生じさせ、及び、この場合には、ブレードからの乱気流によって生じさせられる励起高調波（ｅｘｃｉｔａｔｉｏｎ ｈａｒｍｏｎｉｃ）に対してそのケーシング自体の共振周波数が一致する時に、ケーシングが共振状態となる。こうした状況では、複合材料ケーシングを剛体化させることが必要である。   Although the use of a composite casing allows the overall weight of the engine to be reduced, this reduction in weight reduces the resonant frequency of the casing, and this can lead to turbulence from the fan blades and And, in this case, when the resonance frequency of the casing itself matches the excitation harmonic caused by the turbulence from the blade, the casing is in resonance. Become. Under these circumstances, it is necessary to make the composite casing rigid.

米国特許第８３２２９７１号明細書US Pat. No. 8,322,971

本発明の目的が、ガスタービンケーシングのサイズと重量とを大きく増大させることなしに、増大した剛性を有する、複合材料で作られたガスタービンケーシングを提案することである。   It is an object of the present invention to propose a gas turbine casing made of composite material having increased stiffness without greatly increasing the size and weight of the gas turbine casing.

この目的は、マトリックス（ｍａｔｒｉｘ）で高密度化された補強材（ｒｅｉｎｆｏｒｃｅｍｅｎｔ）を備える複合材料で作られており、且つ、回転体の形状である、ガスタービンケーシングにおいて、ケーシングの内側表面内に環状凹みを形成するように、補剛材部分（ｓｔｉｆｆｅｎｅｒ ｐｏｒｔｉｏｎ）に隣接している、ケーシングの上流部分及び下流部分の半径よりも大きい半径において延びる、少なくとも１つの補剛材部分を備えることを特徴とする、タービンケーシングによって実現される。   The purpose of this is in a gas turbine casing, which is made of a composite material comprising a matrix densified reinforcement and is in the form of a rotating body, annular in the inner surface of the casing. At least one stiffener portion extending at a radius greater than the radius of the upstream and downstream portions of the casing adjacent to the stiffener portion so as to form a recess. Realized by a turbine casing.

通常はケーシングの内側表面全体によって画定されている空気流通路の輪郭に従わない、ケーシングの輪郭において少なくとも１つの段を形成することによって、本発明のケーシングは、局所的に自己補剛を実現する特定の形状を有する。したがって、本発明のケーシングは、ケーシングの製造をより複雑化し且つケーシングの総重量を増大させる、複合材料ケーシング上に取り付けられる専用の補剛材のような、追加的な要素を付加することなしに、剛性の増大を実現する。   By forming at least one step in the contour of the casing that does not normally follow the contour of the airflow passage defined by the entire inner surface of the casing, the casing of the present invention provides self-stiffening locally. Have a specific shape. Thus, the casing of the present invention does not add additional elements, such as dedicated stiffeners mounted on composite casings, that further complicate the manufacture of the casing and increase the total weight of the casing. Realize increased rigidity.

本発明のケーシングの一側面では、各々の補剛材部分は、その横断面において、オメガ形の形状を有する。   In one aspect of the casing of the present invention, each stiffener portion has an omega shape in its cross section.

有利には、各々の補剛材部分によって形成される環状凹みは、各々の補剛材部分に隣接しているケーシングの上流部分及び下流部分の間でのケーシングの内側表面の連続性を実現するために、充填材材料又は構造を充填されている。   Advantageously, the annular recess formed by each stiffener portion provides continuity of the inner surface of the casing between the upstream and downstream portions of the casing adjacent to each stiffener portion. In order to be filled with filler material or structure.

さらに、有利には、各々の補剛材部分によって形成される環状凹みは、音響減衰材料又は構造を充填されている。   Furthermore, advantageously, the annular recess formed by each stiffener part is filled with an acoustic damping material or structure.

本発明のケーシングの別の側面では、ケーシングは、そのケーシングの他の部分よりも大きい厚さを有する滞留区域（ｒｅｔｅｎｔｉｏｎ ｚｏｎｅ）を含み、１つ又は複数の上記補剛材部分は滞留区域の外側に位置している。   In another aspect of the casing of the present invention, the casing includes a retention zone having a thickness greater than other portions of the casing, and the one or more stiffener portions are outside the retention zone. Is located.

本発明は、さらに、本発明のファン滞留ケーシングを有するガスタービン航空機用エンジンと、１つ又は複数のこうした航空機用エンジンを有する航空機とを提供する。   The present invention further provides a gas turbine aircraft engine having the fan retention casing of the present invention and an aircraft having one or more such aircraft engines.

本発明は、さらに、複合材料でガスタービンケーシングを製造する方法を提供し、この方法は、３次元織り又は多層織りによって一体状のストリップの形状に繊維織物（ｆｉｂｅｒ ｔｅｘｔｕｒｅ）を織ることと、サポートツーリング（ｓｕｐｐｏｒｔ ｔｏｏｌｉｎｇ）上に上記繊維織物を巻き付けることによって上記繊維織物を成形することと、マトリックスによって繊維補強材を高密度化することとを含み、及び、この方法は、成形中に、段状部分（ｓｔｅｐｐｅｄ ｐｒｏｔｉｏｎ）に隣接している繊維プリフォームの上流部分及び下流部分の半径よりも大きい半径において延びる、少なくとも１つの段状部分を有する繊維プリフォームを得るように、繊維織物が成形され、及び、上記段状部分は、高密度化の後に、ケーシングの内側表面に環状凹みを形成することを特徴とする。   The present invention further provides a method of manufacturing a gas turbine casing from a composite material, the method comprising weaving a fiber texture in the form of a unitary strip by means of a three-dimensional weave or a multi-layer weave, and a support Forming the fiber fabric by wrapping the fiber fabric on support tooling, densifying the fiber reinforcement with a matrix, and the method includes stepping during molding The fiber fabric is shaped to obtain a fiber preform having at least one stepped portion that extends at a radius greater than the radius of the upstream and downstream portions of the fiber preform adjacent to the stepped portion; And the stepped portion is formed in the casing after the densification. And forming an annular recess in the surface.

本発明の方法の一側面では、各々の補剛材部分は、横断面において、オメガ形の形状を有する。   In one aspect of the method of the present invention, each stiffener portion has an omega shape in cross section.

有利には、各々の補剛材部分によって形成される環状凹みは、各々の補剛材部分に隣接しているケーシングの上流部分及び下流部分の間でのケーシングの内側表面の連続性を実現するために、充填材材料又は構造を充填されている。   Advantageously, the annular recess formed by each stiffener portion provides continuity of the inner surface of the casing between the upstream and downstream portions of the casing adjacent to each stiffener portion. In order to be filled with filler material or structure.

さらに、有利には、各々の補剛材部分によって形成される環状凹みは、音響減衰材料又は構造を充填されている。   Furthermore, advantageously, the annular recess formed by each stiffener part is filled with an acoustic damping material or structure.

本発明の方法の別の側面では、繊維プリフォームは、ケーシング内の滞留区域を形成する、繊維プリフォームの他の部分よりも大きい厚さを有する区域を含み、及び、上記１つ又は複数の段状部分は、このより大きい厚さの部分の外側に位置している。   In another aspect of the method of the present invention, the fiber preform includes an area having a thickness greater than other portions of the fiber preform that forms a residence area in the casing, and the one or more of the above The stepped portion is located outside this larger thickness portion.

本発明の他の特徴と利点とが、添付図面を参照しながら行われる、非限定的な具体例として示されている本発明の特定の実施形態の以下の説明から明らかになる。   Other features and advantages of the present invention will become apparent from the following description of specific embodiments of the invention, illustrated by way of non-limiting illustration, made with reference to the accompanying drawings.

本発明の実施形態による航空機用エンジンの斜視図である。1 is a perspective view of an aircraft engine according to an embodiment of the present invention. 図１のエンジンのファンケーシングの、横断面における片側断面図である。It is a half sectional view in the cross section of the fan casing of the engine of FIG. 本発明の別の実施形態によるファンケーシングの横断面における片側断面図である。It is a half sectional view in the cross section of the fan casing by another embodiment of the present invention. 図２のファンケーシングの補強材を形成するために成形されている繊維織物を示す斜視図である。It is a perspective view which shows the textile fabric currently shape | molded in order to form the reinforcement material of the fan casing of FIG. 図４に示されている繊維織物を巻くことによって得られる図２のケーシングのプリフォームの横断面における片側断面図である。FIG. 5 is a half sectional view of a cross section of the preform of the casing of FIG. 2 obtained by winding the textile fabric shown in FIG. 4. 図４に示されている繊維織物を巻くことによって得られる図２のケーシングのプリフォーム上の噴射セクターの位置決めを示す断面図である。FIG. 5 is a cross-sectional view showing the positioning of the injection sector on the preform of the casing of FIG. 2 obtained by winding the textile fabric shown in FIG. 4.

本発明は、概して、有機マトリックス複合材料で作られているあらゆるガスタービンケーシングに適用される。   The present invention applies generally to any gas turbine casing made of an organic matrix composite material.

以下では、本発明を、ガスタービン航空機用エンジンのためのファンケーシングに対する適用との関連において説明する。   In the following, the invention will be described in the context of application to a fan casing for a gas turbine aircraft engine.

図１に概略的に示すこのようなエンジンは、ガス流の流動方向において上流から下流に、エンジンの入口に配置されているファン１と、圧縮機２と、燃焼室３と、高圧タービン４と、低圧タービン５とを備える。   Such an engine, schematically shown in FIG. 1, has a fan 1, a compressor 2, a combustion chamber 3, and a high-pressure turbine 4 arranged at the inlet of the engine from upstream to downstream in the direction of gas flow. And a low-pressure turbine 5.

このエンジンは、このエンジンの様々な要素に対応する複数の部分を備えるケーシングの内側に収容されている。したがって、ファン１は、回転体の形状であるファンケーシング１０によって取り囲まれている。   The engine is housed inside a casing having a plurality of portions corresponding to the various elements of the engine. Therefore, the fan 1 is surrounded by the fan casing 10 which is the shape of a rotating body.

図２は、ファンケーシング１０の（横断面における）輪郭を示し、及び、ファンケーシング１０は、この例では、有機マトリックス複合材料で作られており、即ち、例えば、炭素繊維、ガラス繊維、アラミド繊維、又は、セラミック繊維のような繊維で作られている補強材から作られており、且つ、例えばエポキシマトリックス、ビスマレイミドマトリックス、又は、ポリイミドマトリックスのようなポリマーマトリックスによって高密度化されている。複合材料からケーシングを製造することは、特に、米国特許ＵＳ８３２２９７１号に説明されている。このケーシングの内側表面１１は、エンジンの空気入口通路を画定する。   FIG. 2 shows the profile (in cross-section) of the fan casing 10 and the fan casing 10 is made of an organic matrix composite material in this example, ie, for example, carbon fiber, glass fiber, aramid fiber Or made from a reinforcement made of fibers such as ceramic fibers and densified by a polymer matrix such as an epoxy matrix, bismaleimide matrix or polyimide matrix. The production of casings from composite materials is described in particular in US Pat. No. 8,322,971. The inner surface 11 of the casing defines an air inlet passage for the engine.

ケーシング１０は、このケーシングが他の要素と共に取り付けられ且つ他の要素に連結されることを可能にするために、このケーシングの上流端部と下流端部とに外側フランジ１４、１５を備えてもよい。このケーシング１０の上流端部と下流端部との間では、ケーシング１０は、変化する厚さを有し、及び、ケーシングの部分１６が末端部分よりも厚く、且つ、末端部分に段階的に到達する。エンジンの入口において吸い込まれるか、又は、ファンのブレードに対する損傷の結果として生じ且つファンの回転によって半径方向に放出される、破片、粒子、又は、物体が、ケーシングの中を通過して航空機の他の部品を破損することを防止するために、こうした破片、粒子、又は、物体を滞留させることが可能である滞留区域を形成するように、部分１６は、上流から下流にファンのための位置を横切って延びる。   The casing 10 may also be provided with outer flanges 14, 15 at the upstream and downstream ends of the casing to allow the casing to be attached with and connected to other elements. Good. Between the upstream end and the downstream end of the casing 10, the casing 10 has a varying thickness, and the casing portion 16 is thicker than the end portion and reaches the end portion in stages. To do. Debris, particles, or objects that are sucked in at the engine inlet or as a result of damage to the blades of the fan and released radially by the rotation of the fan pass through the casing and other parts of the aircraft In order to prevent these parts, the part 16 has a position for the fan from upstream to downstream so as to form a staying area where such debris, particles or objects can stay. Extend across.

本発明では、ケーシング１０は、さらに、ケーシング１０の内側表面１１内に環状凹み１７１を形成するように、補剛材部分１７に隣接しているケーシングの上流部分１８と下流部分１９の半径よりも大きい半径において延びる補剛材部分１７も有する。さらに明確に述べると、補剛材部分１７は、ケーシングの内側表面１１に比べてケーシングの外側に向かって半径方向にオフセットしている環状プラトー（ａｎｎｕｌａｒ ｐｌａｔｅａｕ）１７３によって形成されている。この環状プラトー１７３は、それぞれの環状ライザー（ａｎｎｕｌａｒ ｒｉｓｅｒ）１７２、１７４を介して、ケーシングの内側表面１１の一部分を画定する上流部分１８と下流部分１９とに連結されている。ライザー１７２、１７４と上流部分１８と下流部分１９との間にそれぞれに形成される角度＊172、＊174が、９０°よりも大きく且つ１８０°よりも小さいことが好ましい。これらの角度は、特に、ケーシングに対して与えられることが望ましい剛性に応じて、且つ、製造可能性に応じて、画定される。 In the present invention, the casing 10 further includes a radius of the upstream portion 18 and the downstream portion 19 of the casing adjacent to the stiffener portion 17 so as to form an annular recess 171 in the inner surface 11 of the casing 10. It also has a stiffener portion 17 that extends at a large radius. More specifically, the stiffener portion 17 is formed by an annular plateau 173 that is radially offset toward the outside of the casing relative to the inner surface 11 of the casing. The annular plateau 173 is connected to an upstream portion 18 and a downstream portion 19 that define a portion of the inner surface 11 of the casing via respective annular risers 172, 174. Preferably, the angles * 172 , * 174 formed between the risers 172, 174 and the upstream portion 18 and the downstream portion 19 are larger than 90 ° and smaller than 180 °. These angles are defined in particular according to the stiffness desired to be imparted to the casing and according to manufacturability.

ケーシングの内側表面１１に対する補剛材部分１７の半径方向のオフセットに対応するプラトーの高さＨ173も、ケーシングがエンジンの環境に一体化されることを可能にするための、ケーシングのサイズに対する制約条件を計算に入れながら、ケーシングに与えられることが望ましい剛性に応じて決定される。 The plateau height H 173 corresponding to the radial offset of the stiffener portion 17 relative to the inner surface 11 of the casing is also a constraint on the size of the casing to allow the casing to be integrated into the engine environment. While taking into account the conditions, it is determined according to the stiffness desired to be imparted to the casing.

説明している本実施形態では、プラトー１７３とライザー１７２、１７４は、直線状である横断面における輪郭を有する。しかし、変形例の実施形態では、これらの要素は、わずかに湾曲しているか又は起伏している輪郭を同様に有することも可能である。   In the present embodiment being described, the plateau 173 and the risers 172, 174 have a profile in a cross section that is linear. However, in alternative embodiments, these elements can have slightly curved or undulating profiles as well.

説明している本実施形態では、補剛材部分１７はオメガ形の形状を有し、及び、このオメガ形の形状は、補剛に適切に適合させられている形状である。   In the present embodiment being described, the stiffener portion 17 has an omega shape, and the omega shape is a shape that is appropriately adapted for stiffening.

図３は、補剛材部分２７を画定するプラトー及び環状ライザー２７３、２７３、２７４によって形成されている環状凹み２７１が、この例では、音響減衰を実現する働きをする多孔性構造２７５に相当する、充填材材料又は構造によって充填されているという点において、上述したケーシング１０とは異なる、本発明によるケーシング２０を示す。   FIG. 3 shows that the plateau defining the stiffener portion 27 and the annular recess 271 formed by the annular risers 273, 273, 274 correspond in this example to the porous structure 275 that serves to achieve acoustic damping. Fig. 2 shows a casing 20 according to the invention, which is different from the casing 10 described above in that it is filled with a filler material or structure.

補剛材部分２７によって形成される環状凹み２７１内への充填が、上流部分２８と下流部分２９との間での内側表面２１の連続性を実現し、且つ、したがって、ケーシングの上記内側表面によって画定される通路を変更することを回避する働きをする。この充填は、任意の適切なタイプの材料又は構造を使用して行われてもよく、及び、特に、音響減衰処置を実現する役割を果たす材料（例えば、発泡体）又は構造（例えば、多孔性構造）を使用して行われてもよい。所望の剛性に加えて、補剛材部分のプラトーの高さも、音響的処置のための最適高さに応じて画定されてもよい。   Filling into the annular recess 271 formed by the stiffener portion 27 provides continuity of the inner surface 21 between the upstream portion 28 and the downstream portion 29 and, therefore, by the inner surface of the casing. It serves to avoid changing the defined path. This filling may be performed using any suitable type of material or structure, and in particular, a material (eg, foam) or structure (eg, porous) that serves to achieve an acoustic damping treatment. Structure). In addition to the desired stiffness, the plateau height of the stiffener portion may also be defined according to the optimum height for acoustic treatment.

本発明のケーシングは、上述した補剛材部分１７、２７に類似した複数の補剛材部分を有してもよい。しかし、１つ又は複数の補剛材部分が、上述したケーシング１０、２０のそれぞれの部分１６、２６に相当する追加的な厚さの部分によって形成されている滞留区域の外側に配置されていることが好ましい。   The casing of the present invention may have a plurality of stiffener portions similar to the stiffener portions 17, 27 described above. However, one or more stiffener parts are arranged outside the residence area formed by the additional thickness parts corresponding to the respective parts 16, 26 of the casing 10, 20 described above. It is preferable.

マトリックスによって高密度化された繊維補強材を備える複合材料でケーシング１０を製造する方法を、次で説明する。   A method of manufacturing the casing 10 with a composite material including fiber reinforcements densified with a matrix will be described below.

このケーシングの製造は、ストリップの形状に繊維織物を形成することによって開始する。図４が、航空機用エンジンのケーシングのための繊維プリフォームを形成するストリップの形状に織られている繊維構造１００を非常に概略的に示す。   The production of this casing begins by forming a textile fabric in the form of a strip. FIG. 4 very schematically shows a fiber structure 100 woven in the form of a strip that forms a fiber preform for an aircraft engine casing.

繊維構造１００は、経糸１０１の束、又は、複数の層の形に経糸上に配置されたより糸の束を有し、且つ、経糸が横糸１０２によって相互連結させられる、ジャガード型織機を使用することによって、公知の仕方で行われる３次元織り又は多層織りによって得られる。   The fiber structure 100 uses a jacquard type loom having a bundle of warp yarns 101 or a bundle of strands arranged on the warp yarns in the form of a plurality of layers, and the warp yarns are interconnected by weft yarns 102. Is obtained by three-dimensional weaving or multi-layer weaving performed in a known manner.

示されている例では、３次元織りは、インターロック織り方（ｉｎｔｅｒｌｏｃｋ ｗｅａｖｅ）を用いて行われる。本明細書では、術語「インターロック織り方」は、横糸の各層が複数の経糸層を相互連結し、且つ、特定の横糸列における糸のすべてが織り平面内で同一のずれ（ｍｏｖｅｍｅｎｔ）を有する、織り方を意味する。   In the example shown, the three-dimensional weaving is performed using an interlock weave. As used herein, the term “interlock weave” refers to each weft layer interconnecting a plurality of warp layers and all of the yarns in a particular weft row have the same movement in the weaving plane. Means weaving.

特に国際公開第２００６／１３６７５５号パンフレットに説明されている多層織りのような、他の公知のタイプの多層織りも使用可能である。   Other known types of multi-layer weaves can also be used, such as the multi-layer weave described in WO 2006/136755 in particular.

繊維構造は、特に、炭素繊維、ケイ素炭素繊維（ｓｉｌｉｃｏｎ ｃａｒｂｏｎ ｆｉｂｅｒ）のようなセラミック繊維、ガラス繊維、又は、実際にはアラミド繊維で作られている糸から織られてもよい。   The fiber structure may in particular be woven from yarns made of carbon fibers, ceramic fibers such as silicon carbon fibers, glass fibers or indeed aramid fibers.

図４に示されているように、繊維補強材は、３次元織りによって、変動する厚さを伴う形で形成される繊維織物１００を、マンドレル２００上に巻き付けることによって作られ、及び、このマンドレルは、形成されるべきケーシングの輪郭に一致した輪郭を有する。有利には、繊維補強材は、ケーシング１０のための完全な環状繊維プリフォームを構成し、補剛材部分１７に対応する補剛材を含む単一の部品を形成する。   As shown in FIG. 4, the fiber reinforcement is made by wrapping a fiber fabric 100 formed in a form with varying thickness by a three-dimensional weaving onto a mandrel 200 and the mandrel. Has a contour that matches the contour of the casing to be formed. Advantageously, the fiber reinforcement constitutes a complete annular fiber preform for the casing 10 and forms a single part including the stiffener corresponding to the stiffener portion 17.

このために、マンドレル２００は、形成されるケーシングの内側表面に一致する輪郭の外側表面２０１を有する。繊維織物１００は、マンドレル２００上に巻き付けられることによって、そのマンドレル２００の輪郭にぴったりと嵌め合わされる。マンドレル２００は、その外側表面２０１上に環状の突起２１０を含み、この突起の形状と寸法は、形成される補剛材部分１７の形状と寸法に一致する。マンドレル２００は、さらに、ケーシング１０のフランジ１４、１５に相当する繊維プリフォームの一部分を形成するための２つのチークプレート（ｃｈｅｅｋ−ｐｌａｔｅ）２２０、２３０を有する。   For this purpose, the mandrel 200 has a contoured outer surface 201 that coincides with the inner surface of the casing to be formed. When the fiber fabric 100 is wound on the mandrel 200, the fiber fabric 100 is closely fitted to the contour of the mandrel 200. The mandrel 200 includes an annular protrusion 210 on its outer surface 201, the shape and dimensions of which correspond to the shape and dimensions of the stiffener portion 17 to be formed. The mandrel 200 further has two cheek-plates 220, 230 for forming part of the fiber preform corresponding to the flanges 14, 15 of the casing 10.

図５は、マンドレル２００上の複数の層の形で繊維織物１００を巻き付けた後に得られる繊維プリフォーム３００の断面図である。層又はターン（ｔｕｒｎ）の数は、所望の厚さと繊維織物の厚さとの関数である。この数が少なくとも２つであることが好ましい。この説明している例では、プリフォーム３００は４つの層の繊維織物１００を有する。   FIG. 5 is a cross-sectional view of a fiber preform 300 obtained after winding the fiber fabric 100 in the form of a plurality of layers on the mandrel 200. The number of layers or turns is a function of the desired thickness and the thickness of the textile fabric. This number is preferably at least two. In this illustrated example, the preform 300 has four layers of textile fabric 100.

繊維プリフォーム３００は、段状部分３１０の両側に位置しているプリフォームの上流部分３１１と下流部分３１２との半径よりも大きい半径において延びる段状部分３１０を伴って得られる。段状部分３１０は、ケーシング１０の補剛材部分１７に相当する。繊維プリフォームは、さらに、ケーシングの滞留区域部分１６に相当する、より厚さが大きい部分３２０を有し、及び、末端部分３３０、３４０がケーシングのフランジ１４、１５に相当する。   The fiber preform 300 is obtained with stepped portions 310 extending at a radius greater than the radii of the upstream and downstream portions 311 and 312 of the preform located on either side of the stepped portion 310. The stepped portion 310 corresponds to the stiffener portion 17 of the casing 10. The fiber preform further has a thicker portion 320 corresponding to the residence area portion 16 of the casing, and the end portions 330, 340 correspond to the flanges 14, 15 of the casing.

この後に、繊維プリフォーム３００はマトリックスによって高密度化される。   After this, the fiber preform 300 is densified by the matrix.

繊維プリフォームを高密度化することが、マトリックスを構成する材料を使用して、繊維プリフォームの体積の一部分又は全部において、繊維プリフォームの孔を充填することにある。   The densification of the fiber preform consists in filling the pores of the fiber preform in part or all of the volume of the fiber preform using the material constituting the matrix.

このマトリックスは、液体技術を使用することによって公知の仕方で得られてもよい。   This matrix may be obtained in a known manner by using liquid technology.

この液体技術は、マトリックスの材料の有機前駆物質を含む液体組成物でプリフォームを含浸することにある。この有機前駆物質は、通常は、恐らくは溶媒中に希釈されている、樹脂のようなポリマーの形態である。繊維プリフォームは、封止状態に密閉されることが可能であり且つ最終成形部品の形状を有する空洞を有する、金型の中に入れられる。図６に示されているように、この例では、繊維プリフォーム３００は、金型カバーを形成する複数のセクター２４０と、支持物を形成するマンドレル２００との間に入れられ、及び、これらの要素は、作られるケーシングの外側形状と内側形状とをそれぞれに有する。その後に、例えば樹脂のようなマトリックスの液体前駆物質が、プリフォームの繊維部分全体に含浸するように、空洞全体の中に注入される。   This liquid technique consists in impregnating the preform with a liquid composition comprising an organic precursor of the matrix material. This organic precursor is usually in the form of a resin-like polymer, presumably diluted in a solvent. The fiber preform is placed in a mold that can be sealed in a sealed state and has a cavity having the shape of the final molded part. In this example, as shown in FIG. 6, the fiber preform 300 is placed between a plurality of sectors 240 forming a mold cover and a mandrel 200 forming a support, and these The elements each have an outer shape and an inner shape of the casing to be made. Thereafter, a matrix liquid precursor, such as a resin, is injected into the entire cavity so as to impregnate the entire fiber portion of the preform.

この前駆物質は、熱処理によって、即ち、一般的には、金型を加熱し、溶剤すべてを除去してポリマーを硬化させた後に、形成される部品の形状に一致する形状を有する金型の中にプリフォームを保持し続けることによって、有機マトリックスに変形させられ、即ち、重合させられる。この有機マトリックスは、特に、例えば市販されている高性能エポキシ樹脂のようなエポキシ樹脂、又は、炭素マトリックス又はセラミックマトリックスのための液体前駆物質から得られてもよい。   This precursor is contained in a mold having a shape that matches the shape of the part being formed by heat treatment, ie, generally after heating the mold and removing all of the solvent to cure the polymer. By continuing to hold the preform, it is transformed into an organic matrix, i.e. polymerized. This organic matrix may in particular be obtained from an epoxy resin, for example a commercially available high performance epoxy resin, or a liquid precursor for a carbon matrix or a ceramic matrix.

炭素マトリックス又はセラミックマトリックスを形成する場合は、熱処理は、使用される前駆物質と熱分解条件とに応じて、有機マトリックスを炭素マトリックス又はセラミックマトリックスに変形するために、有機前駆物質を熱分解することにある。例えば、炭素の液体前駆物質は、フェノール樹脂のような比較的高いコークス含量（ｃｏｋｅ ｃｏｎｔｅｎｔ）を有する樹脂であってもよく、一方、セラミックの液体前駆物質、特にＳｉＣの液体前駆物質は、ポリカルボシラン（ＰＣＳ）、又は、ポリチタノカルボシラン（ＰＴＣＳ）、又は、ポリシラザン（ＰＺＳ）のタイプの樹脂であってもよい。含浸から熱処理への複数の連続的サイクルが、所望の度合の高密度化を実現するために行われてもよい。   When forming a carbon matrix or ceramic matrix, the heat treatment may pyrolyze the organic precursor to transform the organic matrix into a carbon matrix or ceramic matrix, depending on the precursor used and the pyrolysis conditions. It is in. For example, a carbon liquid precursor may be a resin having a relatively high coke content, such as a phenolic resin, while a ceramic liquid precursor, particularly a SiC liquid precursor, is a polycarbohydrate. It may be a silane (PCS), or polytitanocarbosilane (PTCS), or polysilazane (PZS) type resin. Multiple successive cycles from impregnation to heat treatment may be performed to achieve the desired degree of densification.

本発明の一側面では、繊維プリフォームは、公知の樹脂トランスファー成形（ＲＴＭ）法によって高密度化されてもよい。ＲＴＭ法では、繊維プリフォームは、作られるケーシングの形状を有する金型の中に入れられる。熱硬化性樹脂が、硬質材料部分と金型との間に画定されており且つ繊維プリフォームを収容する内側空間の中に注入される。樹脂によるプリフォームの含浸を調整し最適化するために、一般的には、圧力勾配が、樹脂が注入される場所と樹脂放出オリフィスとの間のこの内側空間内に設定される（ｓｅｔ ｕｐ）。   In one aspect of the present invention, the fiber preform may be densified by a known resin transfer molding (RTM) method. In the RTM method, the fiber preform is placed in a mold having the shape of the casing to be made. A thermosetting resin is injected into the inner space defined between the hard material portion and the mold and containing the fiber preform. In order to adjust and optimize the impregnation of the preform with the resin, typically a pressure gradient is set up in this inner space between where the resin is injected and the resin discharge orifice. .

一例として、使用される樹脂はエポキシ樹脂であってもよい。ＲＴＭ法に適している樹脂が公知である。こうした樹脂は、繊維の中へのこの樹脂の注入を容易化するために、低い粘度を有する。樹脂の温度等級及び／又は化学的性質は、その部品が受けることになる熱機械応力の関数として決定される。この樹脂は、補強材全体に注入され終わると、ＲＴＭ法に準拠した熱処理によって重合させられる。   As an example, the resin used may be an epoxy resin. Resins suitable for the RTM method are known. Such resins have a low viscosity in order to facilitate the injection of this resin into the fibers. The temperature grade and / or chemistry of the resin is determined as a function of the thermomechanical stress that the part will experience. When the resin is injected into the entire reinforcing material, it is polymerized by a heat treatment according to the RTM method.

注入と重合との後に、その部品は金型から外される。最後に、その部品は、過剰な樹脂を取り除くために削られ、及び、図１と図２に示すように、ケーシング１０を得るために面取り箇所が機械加工される。   After injection and polymerization, the part is removed from the mold. Finally, the part is shaved to remove excess resin and the chamfered portion is machined to obtain the casing 10 as shown in FIGS.

１０ ガスタービンケーシング
１１ ケーシングの内側表面
１６ 滞留区域
１７、２７ 補剛材部分
１８ ケーシングの上流部分
１９ ケーシングの下流部分
１００ 繊維織物
１７１、２７１ 環状凹み
２７５ 音響減衰材料又は構造 DESCRIPTION OF SYMBOLS 10 Gas turbine casing 11 Casing inner surface 16 Residence area 17, 27 Stiffener part 18 Casing upstream part 19 Casing downstream part 100 Textile fabric 171 271 Annular dent 275 Sound damping material or structure

Claims (12)

マトリックスによって高密度化された補強材を備える複合材料で作られており、且つ、回転体の形状である、ガスタービンケーシング（１０）において、
このガスタービンケーシング（１０）の内側表面（１１）内に環状凹み（１７１）を形成するように、補剛材部分（１７）に隣接しているこのケーシングの上流部分及び下流部分（１８、１９）の半径よりも大きい半径において延びる、少なくとも１つの補剛材部分（１７）を備えることを特徴とするガスタービンケーシング（１０）。 In the gas turbine casing (10), which is made of a composite material with reinforcements densified by a matrix and is in the form of a rotating body,
The upstream and downstream portions (18, 19) of the casing adjacent to the stiffener portion (17) so as to form an annular recess (171) in the inner surface (11) of the gas turbine casing (10). The gas turbine casing (10), characterized in that it comprises at least one stiffener part (17) extending at a radius greater than the radius of. 各々の補剛材部分（１７）は、横断面において、オメガ形の形状を有することを特徴とする請求項１に記載のケーシング。   2. A casing as claimed in claim 1, characterized in that each stiffener part (17) has an omega shape in cross section. 各々の補剛材部分（２７）によって形成されている前記環状凹み（２７１）は、各々の補剛材部分（２７）に隣接している前記ケーシング（２０）の前記上流部分及び下流部分（２８、２９）の間での前記ケーシング（２０）の内側表面（２１）の連続性を実現するために、充填材材料又は構造（２７５）を充填されていることを特徴とする請求項１又は２に記載のケーシング。   The annular recess (271) formed by each stiffener portion (27) is connected to the upstream and downstream portions (28) of the casing (20) adjacent to each stiffener portion (27). 29) filled with a filler material or structure (275) to achieve continuity of the inner surface (21) of the casing (20) between Casing described in. 各々の補剛材部分（２７）によって形成されている前記環状凹み（２７１）は、音響減衰材料又は構造（２７５）を充填されていることを特徴とする請求項１又は２に記載のケーシング。   A casing according to claim 1 or 2, characterized in that the annular recess (271) formed by each stiffener part (27) is filled with an acoustic damping material or structure (275). 前記ケーシング（１０）は、前記ケーシング（１０）の他の部分よりも大きい厚さを有する滞留区域（１６）を含み、及び、１つ又は複数の前記補剛材部分（１７）は前記滞留区域（１６）の外側に位置していることを特徴とする請求項１〜４のいずれか１項に記載のケーシング。   The casing (10) includes a retention zone (16) having a thickness greater than other portions of the casing (10), and one or more stiffener portions (17) are the retention zone. It is located in the outer side of (16), The casing of any one of Claims 1-4 characterized by the above-mentioned. 請求項１〜５のいずれか１項に記載のファン滞留ケーシング（１０）を有するガスタービン航空機用エンジン。   A gas turbine aircraft engine comprising the fan retention casing (10) according to any one of claims 1-5. 請求項６に記載の１つ又は複数のエンジンを有する航空機。   An aircraft having one or more engines according to claim 6. 複合材料で作られたガスタービンケーシング（１０）を製造する方法であって、３次元又は多層織りによって一体状のストリップの形状に繊維織物（１００）を織る段階と、サポートツーリング（２００）上に前記繊維織物を巻き付けることによって前記繊維織物を成形することと、マトリックスによって繊維補強材（３００）を高密度化する段階とを含む方法において、
成形中に、段状部分（３１０）に隣接している繊維プリフォーム（３００）の上流部分及び下流部分（３１１、３１２）の半径よりも大きい半径において延びる、少なくとも１つの段状部分（３１０）を有する前記繊維プリフォーム（３００）を得るように、前記繊維織物（１００）が成形され、及び、前記段状部分は、高密度化の後に、前記ガスタービンケーシング（１０）の内側表面（１１）内に環状凹み（１７１）を形成することを特徴とする方法。 A method of manufacturing a gas turbine casing (10) made of composite material, the step of weaving a fiber fabric (100) in the form of a unitary strip by means of a three-dimensional or multi-layer weave, and on a support tooling (200) Forming the fiber fabric by wrapping the fiber fabric and densifying the fiber reinforcement (300) with a matrix;
At least one stepped portion (310) that extends during molding at a radius that is greater than the radius of the upstream and downstream portions (311, 312) of the fiber preform (300) adjacent to the stepped portion (310). The fiber woven fabric (100) is shaped to obtain the fiber preform (300) having, and after the densification, the stepped portion is formed on the inner surface (11) of the gas turbine casing (10). ) To form an annular recess (171). 各々の補剛材部分（１７）は、横断面において、オメガ形の形状を有することを特徴とする請求項８に記載の方法。   9. Method according to claim 8, characterized in that each stiffener part (17) has an omega-shaped shape in cross section. 各々の補剛材部分（１７）によって形成されている前記環状凹みは、各々の補剛材部分（２７）に隣接している前記ケーシング（２０）の前記上流部分及び下流部分（２８、２９）の間での前記ケーシング（２０）の前記内側表面（２１）の連続性を実現するように、充填材材料又は構造（２７５）を充填されていることを特徴とする請求項８又は９に記載の方法。   The annular recess formed by each stiffener portion (17) is connected to the upstream and downstream portions (28, 29) of the casing (20) adjacent to each stiffener portion (27). 10. Filled with filler material or structure (275) so as to achieve continuity of the inner surface (21) of the casing (20) between them. the method of. 各々の補剛材部分（２７）によって形成されている前記環状凹み（２７１）は、音響減衰材料又は構造（２７５）を充填されていることを特徴とする請求項８又は９に記載の方法。   10. A method according to claim 8 or 9, characterized in that the annular recess (271) formed by each stiffener part (27) is filled with an acoustic damping material or structure (275). 前記繊維プリフォーム（３００）は、前記ケーシング（１０）内の滞留区域（１６）を形成するように、前記繊維プリフォームの他の部分よりも大きい厚さを有する区域（３２０）を有し、前記１つ又は複数の段状部分（３１０）は、前記より大きい厚さの部分（３２０）の外側に位置していることを特徴とする請求項８〜１１のいずれか１項に記載の方法。   The fiber preform (300) has an area (320) having a thickness greater than other parts of the fiber preform so as to form a residence area (16) in the casing (10); 12. A method according to any one of claims 8-11, wherein the one or more stepped portions (310) are located outside the larger thickness portion (320). .
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JP6734261B2 (en) 2020-08-05
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